Apparatus and method for monitoring performance characteristics of a component of a vehicle

ABSTRACT

An apparatus for monitoring at least one performance characteristic of a component of a vehicle may include a tripod connected to an exterior surface of the vehicle, the tripod includes a plurality of airfoils defining an aerodynamic surface of the tripod, a camera positioned on the tripod at a predetermined viewing angle directed toward the component of the vehicle and a camera fairing connected to the tripod and surrounding the camera, the camera fairing includes a sidewall defining an aerodynamic surface of the camera fairing, an aperture disposed through the sidewall and aligned with the camera and a plurality of protrusions positioned proximate the aperture.

PRIORITY

This application is a divisional of U.S. Ser. No. 14/263,017 filed onApr. 28, 2014.

FIELD

The present disclosure is generally related to monitoring performance ofa vehicle and, more particularly, to an apparatus and method forvisually monitoring one or more performance characteristics of acomponent of a vehicle, such as a wing assembly of an aircraft.

BACKGROUND

Performance testing of a vehicle is common prior to placing the vehicleinto use, for example, in the aerospace industry. For example,performance characteristics of components (e.g., wing assemblies) of anaircraft need to be observed and/or recorded during flight.

Various methods are employed to monitor inflight performancecharacteristics. For example, a camera may be mounted inside the cabinor in the tail of the aircraft to record performance of a wing test inflight conditions. However, interior cameras often fail to provideoptimum viewing angles of the desired component. As another example, torecord performance of a wing test in flight conditions, a chase aircraftmay carry a camera. However, cameras mounted on chase aircraft lackimage stability and/or suitable image resolution. A camera mountedexternally on the aircraft and displaced from tested component mayprovide suitable viewing angles, but experience airflow-inducedvibrations that degrade resulting image quality.

Accordingly, those skilled in the art continue with research anddevelopment efforts in the field of monitoring and/or recordingperformance characteristics of a vehicle, such an aircraft in flightconditions.

SUMMARY

In one embodiment, the disclosed apparatus for monitoring at least oneperformance characteristic of a component of a vehicle may include acamera fairing defining an internal volume, the camera fairing mayinclude a sidewall including an aerodynamic surface and an aperturedisposed through the sidewall, wherein the aerodynamic surface includesa plurality of protrusions positioned proximate the aperture.

In another embodiment, the disclosed apparatus for monitoring at leastone performance characteristic of a component of a vehicle may include atripod including an aerodynamic surface, the tripod may include a firstleg directed toward a forward end of the vehicle, a second leg directedtoward an aft end of the vehicle, and a third leg directed toward theaft end of the vehicle, wherein each of the first leg, the second legand the third leg are disposed at a non-zero sweep angle with respect toa plane normal to a streamline direction, wherein the third leg isoffset with respect to the second leg, and wherein the second leg andthe third leg are disposed at a non-zero splay angle with respect to oneanother.

In another embodiment, the disclosed apparatus for monitoring at leastone performance characteristic of a wing assembly of an aircraft mayinclude a tripod connected to an exterior surface of an aircraft, thetripod includes a plurality of airfoils defining an aerodynamic surfaceof the tripod, a camera positioned on the tripod at a predeterminedviewing angle directed toward a wing assembly of the aircraft and acamera fairing connected to the tripod and surrounding the camera, thecamera fairing includes a sidewall defining an aerodynamic surface ofthe camera fairing, an aperture disposed through the sidewall andaligned with the camera and a plurality of protrusions positionedproximate the aperture.

In yet another embodiment, also disclosed is a method for monitoring atleast one performance characteristic of a wing assembly of an aircraft,the method may include the steps of: (1) connecting a tripod to anexterior surface of the aircraft, the tripod including a plurality ofairfoils defining an aerodynamic surface of the tripod, (2) positioninga camera on the tripod at a predetermined viewing angle directed towardthe wing assembly, (3) connecting a camera fairing to the tripodsurrounding the camera, the camera fairing including a sidewall definingan aerodynamic surface of the camera fairing, an aperture disposedthrough the sidewall and aligned with the camera and a plurality ofprotrusions positioned proximate the aperture and recording at least oneperformance characteristic of the wing assembly during flight.

Other embodiments of the disclosed apparatus will become apparent fromthe following detailed description, the accompanying drawings and theappended claims.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a schematic illustration of the disclosed apparatus formonitoring at least one performance characteristic of a component of avehicle;

FIG. 2 is a schematic illustration of one implementation of thedisclosed apparatus;

FIG. 3 is a side perspective view of one embodiment of the tripodassembly and camera fairing of the disclosed apparatus;

FIG. 4 is a schematic side view of one embodiment of the tripod of thetripod assembly with respect to a reference plane normal to a streamlinedirection;

FIG. 5 is a schematic side view of one embodiment of the tripod of thetripod assembly with respect to an exterior surface of the vehicle;

FIG. 6 is a schematic rear view of the tripod;

FIG. 7 is a schematic view, in section, of one embodiment of the leg ofthe tripod;

FIG. 8 is a partial front and side perspective view of one embodiment ofthe support strut and mount fitting of the tripod assembly;

FIG. 9 is a partial side elevational view of the tripod and the camerafairing of the disclosed apparatus;

FIG. 10 is a partial side elevational view of the camera enclosure andcamera of the disclosed apparatus;

FIG. 11 is schematic view of a seal grommet of the disclosed apparatus10;

FIG. 12 is a front and side perspective view of one embodiment of thecamera fairing;

FIG. 13 is a partial side elevational view of the camera fairing;

FIG. 14 is a partial front elevational view of the camera fairing;

FIG. 15 is a partial schematic illustration, in section, of oneembodiment of the plurality of protrusions of the camera fairing;

FIG. 16 is a partial side view of the protrusion; and

FIG. 17 is a flow diagram of one embodiment of the disclosed method formonitoring at least one performance characteristic of a wing assembly ofan aircraft.

DETAILED DESCRIPTION

The following detailed description refers to the accompanying drawings,which illustrate specific embodiments of the disclosure. Otherembodiments having different structures and operations do not departfrom the scope of the present disclosure. Like reference numerals mayrefer to the same element or component in the different drawings.

Referring to FIG. 1, the disclosed apparatus, generally designated 10,for monitoring at least one performance characteristic and/or feature ofa component (e.g., a wing assembly) of a vehicle (e.g., an aircraft) mayinclude a tripod assembly 12, a camera fairing 14, and an imaging system16. The imaging system 16 may include a camera 18.

The apparatus 10 may monitor (e.g., visually observe and/or record) oneor more performance characteristics and/or features of a component 20 ofa vehicle 24. For example, the apparatus 10 may monitor operationalperformance characteristics of the vehicle 24 including, but not limitedto, structural deflection, ice accumulation, thermal characteristics ofairflow, thermal characteristics of the component 20 (e.g., the wingassembly) or the like. The camera 18 may include video camera or a stillphotograph camera. The camera 18 may obtain videos or images in thevisible spectrum or the infrared spectrum.

The tripod assembly 12 may be connected to an exterior surface 22 of thevehicle 24. The camera fairing 14 may be connected to the tripodassembly 12. The camera 18 may be positioned within the camera fairing14. The tripod assembly 12 may support the camera 18 at a predeterminedposition such that a line of sight 26 of the camera 18 includes aviewing angle 28 with respect to a reference plane 30. In the exampleillustrated in FIG. 1, the reference plane 30 may be substantiallyhorizontal; however, those skilled in the art will appreciate that thereference plane 30 may have any orientation depending upon the component20 being monitored.

Referring briefly to FIGS. 1 and 2, as one example, the viewing angle 28and/or the reference plane 30 (FIG. 1) may be defined with respect to abody coordinate system 132 of the vehicle 24 (FIG. 2). For example, thebody coordinate system 132 may include an X-axis parallel to alongitudinal axis of the vehicle 24 (e.g., an aircraft 32) and a Y-axisnormal to the X-axis (e.g., generally parallel to the wing assemblies 34of the aircraft 32). The horizontal reference plane 30 may be generallyparallel to an X-Y plane defined by the X-axis and the Y-axis. A Z-axismay be normal to the X-Y plane.

Referring again to FIG. 1, the viewing angle 28 may be a zero angle or anon-zero angle. For example, the viewing angle 28 may be approximately 0degrees. As another example, the viewing angle 28 may be betweenapproximately 1 degree and 90 degrees. As another example, the viewingangle 28 may be between approximately 5 degrees and 60 degrees. Asanother example, the viewing angle 28 may be between approximately 15degrees and 45 degrees. As another example, the viewing angle 28 may beapproximately 16.8 degrees. As yet another example, the viewing angle 28may be approximately 7 degrees.

Referring to FIG. 2, in an example implementation, the vehicle 24 may bethe aircraft 32 and the component 20 may be the wing assembly 34 of theaircraft 32. For example, the apparatus 10 may monitor inflightperformance or simulated inflight performance (e.g., wind tunnel) of thewing assembly 34.

In an example construction, the tripod assembly 12 may be connected tothe exterior surface 22 of the aircraft 32. For example, the tripodassembly 12 may be connected to an exterior surface 22 (e.g., an uppersurface) of a fuselage 37 of the aircraft 32 approximately between thewing assemblies 34. The line of sight 26 of the camera 18 may bedirected toward an area of interest 36 (e.g., an upwardly facingsurface) of the wing assembly 34. For example, reference plane 30(FIG. 1) may be at least partially co-planar with the upwardly facingsurface of the wing assembly 34.

Referring to FIG. 3, the tripod assembly 12 may include aerodynamicsurface 38 and the camera fairing 14 may include aerodynamic surface 40.The aerodynamic surfaces 38, 40 may be suitably shaped to control and/orreduce vibrations upon the camera 18 and preserve image quality obtainedby the camera 18 (FIG. 1) when monitoring the component 20 (FIG. 2)during operation of the vehicle 24 (e.g., during flight).

The tripod assembly 12 may include a tripod 52 including three legs 42(identified individually as a first leg 42 a, a second leg 42 b and athird leg 42 c). For example, the first leg 42 a may define a forwardleg (e.g., being directed toward a forward end of the vehicle 24) andthe second leg 42 b and third leg 42 c may define a pair of aft legs(e.g., being directed toward an aft end of the vehicle 24. As usedherein, the terms forward and aft may be considered relative to adirection of movement of the vehicle 24 (e.g., the aircraft 32).

Each leg 42 may include a lower end 48 (identified individually as lowerends 48 a, 48 b and 48 c) and an upper end 50 (identified individuallyas upper ends 50 a, 50 b and 50 c) longitudinally opposed from the lowerend 48. The lower end 48 of each leg 42 may be connected to the vehicle24. For example, the lower end 48 (e.g., lower ends 48 a, 48 b and 48 c)of each leg 42 (e.g., the first leg 42 a, the second leg 42 b and thethird leg 42 c) may include and/or terminate at a lower attach point 136connected to the exterior surface 22 of the vehicle 24.

The first leg 42 a may be aligned with (e.g., directed into) astreamline direction 46 of the vehicle 24. As used herein, thestreamline direction 46 may be substantially opposite a direction oftravel of the vehicle 24. The second leg 42 b and the third leg 42 c mayextend from the first leg 42 a. For example, the upper ends 50 b, 50 cof the second leg 42 b and the third leg 42 c, respectively, may beconnected to the first leg 42 a between the lower end 48 a and the upperend 50 a.

The second leg 42 b and the third leg 42 c may be offset or staggeredalong a longitudinal axis of the first leg 42 a. For example, the thirdleg 42 c may be positioned above the second leg 42 b. As an example, thesecond leg 42 b may be positioned proximate (e.g., at or near) themiddle of the first leg 42 a and the third leg 42 c may be positionedproximate the upper end 50 a of the first leg 42 a.

Those skilled in the art will recognize that the position of the secondleg 42 b and the third leg 42 c on the first leg 42 a may depend on thedimensions (e.g., length dimension) of the first leg 42 a. As a general,non-limiting example, the second leg 42 b may be connected to the firstleg 42 a at a position approximately ⅔ of the length dimension from thelower end 48 a and the third leg 42 c may be connected to the first leg42 a at a position approximately ⅚ of the length dimension from thelower end 48 a. As a specific, non-limiting example, the first leg 42 amay include a length dimension of approximately 6 feet, the second leg42 b may be connected to the first leg 42 a at a position approximately4 feet from the lower end 48 a and the third leg 42 c may be connectedto the first leg 42 a at a position approximately 5 feet from the lowerend 48 a.

Referring to FIG. 4, each leg 42 (e.g., the first leg 42 a, the secondleg 42 b and the third leg 42 c) may be disposed at a non-zero sweepangle 138 (identified individually as a first sweep angle 138 a, asecond sweep angle 138 b and a third sweep angle 138 c) with respect toa reference plane 134 normal to the streamline direction 46. Forexample, the sweep angles 138 may be approximately between 40 degreesand 60 degrees. As another example, the sweep angles 138 may beapproximately between 45 degrees and 55 degrees. As a specific,non-limiting example, the first sweep angle 138 a may be approximately51.3 degrees and the second sweep angle 138 b and third sweep angle 138c may be approximately 45.2 degrees.

The offset position of the second leg 42 b and the third leg 42 c withrespect to the first leg 42 a and the sweep angles 138 of each leg 42may be configured to substantially reduce and/or eliminate transonicinteractions with the tripod 12. As used herein, transonic may refer toa condition of flight in which a range of velocities of airflow existsurrounding and/or flowing past the legs 42 that are concurrently below,at, and above the speed of sound in a local Mach number range betweenapproximately 0.5 to 1.5. As used herein, local Mach number may refer tothe speed of the airflow proximate (e.g., at or around) the legs 42. Forexample, the sweep angles 138 (e.g., each of the first sweep angle 138a, the second sweep angle 138 b and the third sweep angle 138 c) maydepend upon and/or may be adjusted with respect to various factorsincluding, but not limited to, the local Mach number and the thicknessof the leg 42 (e.g., a cross-sectional thickness of each leg 42 along aY-axis, as described herein below and illustrated in FIG. 7).

Referring to FIG. 5, each leg 42 may be connected to the vehicle 24 at anon-zero lower connection angle 54 with respect to the exterior surface22 (identified individually as a first lower connection angle 54 a, asecond lower connection angle 54 b and a third lower connection angle 54c). The second leg 42 b and the third leg 42 c may be connected to thefirst leg 42 a at a non-zero upper connection angle 56 with respect tothe first leg 42 a (identified individually as a second upper connectionangle 56 a and a third upper connection angle 56 c). Those skilled inthe art will recognize that the lower connection angle 54 and/or theupper connection angles 56 may depend upon the sweep angles 138.

Referring to FIG. 6, the second leg 42 b and the third leg 42 c may bedisposed at a non-zero splay angle 58 with respect to one another. Thesplay angle 58 may depend upon the local Mach number. For example, thesplay angle 58 between the second leg 42 b and the third leg 42 c may beset for a minimum Mach number (e.g., below 1) in order to minimizesupersonic flow and avoid a wake resulting from airflow passing over thefirst leg 42 a. For example, the splay angle 58 may be betweenapproximately 40 degrees and 65 degrees. As another example, the splayangle 58 may be approximately 60.6 degrees.

Referring to FIG. 7, in one example construction, the tripod assembly 12may include an airfoil 44 surrounding internal support struts 60defining each leg 42 of a tripod 52. For example, each leg 42 mayinclude the support strut 60 and the airfoil 44 connected to andsubstantially surrounding the support strut 60. The airfoil 44 maydefine the aerodynamic surface 38 of the tripod assembly 12 (e.g., ofeach leg 42). In one example construction, the aerodynamic surface 38may be smooth. In another example construction, the aerodynamic surface38 may include surface roughness and/or vortex generators.

The airfoil 44 of each leg 42 may include an X-axis and a Y-axis. Theairfoil 44 of each leg 42 may be oriented such that the X-axis issubstantially parallel to the streamline direction 46. For example, theairfoil 44 of each leg 42 may be oriented such that a leading edge 62 ofthe airfoil 44 is aligned with and directed into the airflow. Theairfoil 44 of each leg 42 may be symmetric about both the X-axis and theY-axis. For example, the leading edge 62 and a trailing edge 64 of theairfoil 44 may be substantially the same (e.g., having substantiallyequal radius). The symmetric cross-sectional shape airfoil 44 may limitsteady and unsteady aerodynamic side loads on the leg 42 (e.g., on thestrut 60).

Referring to FIG. 8, the support strut 60 may be connected to thevehicle 24 (e.g., at the lower end 48 of the leg 42). A lower end 68 ofthe support strut 60 may be connected to the vehicle 24 in a non-rigidmanner. The non-rigid connection between the strut 60 and the exteriorsurface 22 of the vehicle 24 (e.g., at the lower attach point 136) mayprovide for minor movement of the strut 60 with respect to the exteriorsurface 22 of the vehicle 24. Such minor movement of the strut 60 mayallow for minor position adjustments of the legs 42 with respect to theexterior surface 22 of the vehicle 24 (e.g., the lower connection angles54), such as in response to flexing of the exterior surface 22 of thevehicle 24 (e.g., during flight of the aircraft 32).

For example, the support strut 60 may be pivotally connected (e.g., viaa pinned connection) to the vehicle 24 at the lower attach point 136. Inan example construction, the lower attach point 136 may include a mountfitting 66 connected to the exterior surface 22 of the vehicle 24. Themount fitting 66 may include a tang 72. The lower end 68 of the supportstrut 60 may include a clevis 70. The tang 72 may be received within aU-shaped portion of the clevis 70 and secured by a pin.

The tripod assembly 12 may be grounded to the vehicle 24. For example,the tripod assembly 12 may include a jumper cable 75 electricallyconnected between the support strut 60 and a grounding bracket 77. Thegrounding bracket 77 may be connected to the exterior surface 22 of thevehicle 24. The jumper cable 75 and the grounding bracket 77 mayminimize or eliminate electromagnetic effects on the tripod assembly 12.

Referring to FIG. 9, in one embodiment, the camera 18 may be connectedto the upper end 50 a of the first leg 42 a. The camera fairing 14 maybe connected to the first leg 42 a surrounding the camera 18. Forexample, the camera 18 and the camera fairing 14 may be connected aboutthe trailing edge 64 of the airfoil 44 of the first leg 42 a. In anexample construction, the camera fairing 14 may include an opening 78suitably sized to receive a portion of the airfoil 44 (e.g., a portionof the trailing edge 64) of the first leg 42 a. The camera fairing 14may include an aperture 76. The aperture 76 may be aligned with a lensof the camera 18 upon the camera fairing 14 being connected to the firstleg 42 of the tripod 52, as further illustrated in FIG. 12.

The tripod 52 may include a head plate 80. The head plate 80 may coverthe upper end of the airfoil 44 and an upper portion of the opening 78in the camera fairing 14, as also illustrated in FIG. 4. The head plate80 may provide an aerodynamic interface between the aerodynamic surface38 of the tripod 52 and the aerodynamic surface 40 of the camera fairing14.

Referring to FIG. 10, in one embodiment, the imaging system 16 mayinclude a camera enclosure 82. The camera 18 may be mounted within thecamera enclosure 82. In an example construction, the camera enclosure 82may include a plurality of sidewalls 84 defining a sealed internalvolume 86. The camera 18 may be housed within the sealed internal volume86 of the camera enclosure 82. The camera enclosure 82 may include anadjustment mechanism 94 interconnected with the camera 18. Theadjustment mechanism 94 may allow for rotational and/or angular positionadjustment (e.g., with respect to the X-Y plane of the body coordinatesystem 132) of the camera 18 within the camera enclosure 82 to optimallyposition the line of sight 26 of the camera 18 at a desired viewingangle 28 (FIG. 2).

In an example construction, the camera enclosure 82 may be connected toan upper end 74 of the support strut 60 of the first leg 42 a. Forexample, the tripod 52 may include a mounting bracket 90 connected tothe upper end 74 of the strut 60 of the first leg 42 a. The cameraenclosure 82 may be connected to the mounting bracket 90. An interfacebetween the camera enclosure 82 and the mounting bracket 90 may includean adjustment fastener 92. The adjustment fastener 92 may allow forposition adjustment of the camera enclosure 82, and thus, the camera 18,with respect to the tripod 52 (e.g., the strut 60).

Referring to FIGS. 1 and 10, a purge system 96 (FIG. 2) may be connectedto the camera enclosure 82 to maintain environmental conditions withinthe sealed internal volume 86 of the camera enclosure 82 to ensure imagequality obtained by the camera 18. For example, a dry nitrogen source 98may be fluidly connected to the camera enclosure 82. Tubing 100 mayfluidly interconnect the dry nitrogen source 98 and the camera enclosure82. The purge system 96 may also include suitable valves 102 and/orconnectors 104.

The imaging system 16 (FIG. 2) may include a computer 106communicatively connected to the camera 18. The computer 106 may recordand/or process images and/or video obtained by the camera 18. Electricalcable 108 may electrically interconnect the computer 106 and the camera18. The electrical cable 108 may transfer power and/or data between thecomputer 106 and the camera 18. The electrical cable 108 may includebraided wire shielding to reduce or eliminate electromagnetic effects onthe imaging system 16 (e.g., the camera 18). The imaging system 16 mayalso include suitable connectors 110.

Referring to FIGS. 1 and 8, in an example implementation, the drynitrogen source 98, the computer 106 and a suitable power supply (notshown) may be located within an interior of the vehicle 24 (e.g., withinthe aircraft 32). The tubing 100 and the electrical cable 108 may extendthrough the exterior surface 22 of the vehicle 24 for connection to thecamera enclosure 82 and the camera 18, respectively. A grommet 112 maybe used to seal a through hole formed through the exterior surface 22through which the tubing 100 and the electrical cable 108 extend. Thetubing 100 and the electrical cable 108 may pass through the grommet 112connected to the exterior surface 22.

Referring to FIG. 11, in an example construction, the grommet 112 may besuitably sized to receive two lines of tubing 100 (e.g., a primarytubing and a spare tubing) and two lines of electrical cable 108 (e.g.,a primary electrical cable and a spare electrical cable). Any gaps 114between the tubing 100, the electrical cable 108 and the grommet 112 maybe filled with a sealant 116. The grommet 112 may include an outer ring118 and a layer of over braid shielding to reduce or eliminateelectromagnetic effects.

Referring to FIGS. 12-14, the camera fairing 14 may include a sidewall122 defining an internal volume 124. The sidewall 122 may include acurved cross-sectional profile defining the aerodynamic surface 40 ofthe camera fairing 14. The aerodynamic surface 40 may be substantiallysmooth. The camera 18 or the camera enclosure 82 and the camera 18 maybe positioned within the internal volume 124, as illustrated in FIG. 12,upon the camera fairing 14 being connected to the first leg 42 a (e.g.,the airfoil 44) of the tripod 52, as illustrated in FIGS. 13 and 14.

The opening 78 (FIG. 12) may be sized in close tolerance to a thicknessdimension of the airfoil 44 of the first leg 42 a (FIGS. 12 and 13). Anyinterfaces 126 (FIGS. 13 and 14) between the edges of the opening 78 ofthe camera fairing 14 and the surface of the airfoil 44 may besubstantially closed to provide an aerodynamic interface between theaerodynamic surface 38 of the airfoil 44 and the aerodynamic surface 40of the camera fairing 14. In an example construction, a sealing strip(e.g., speed tape) may be used to further cover and seal the interfaces126.

The camera fairing 14 may include a plurality of protrusions 128extending or projecting outwardly from the sidewall 122. The protrusions128 may control the airflow passing over and/or into the aperture 76 toreduce noise (e.g., whistling and/or buzzing), vibrations, pressurevariations or any other undesired signal that may negatively impactoptimal image quality obtained by the camera 18 during monitoring of thevehicle 24. The protrusions 128 may be positioned proximate (e.g., at ornear) the aperture 76. For example, the protrusions 128 may bepositioned at least partially around the aperture 76 disposed throughthe sidewall 122. The protrusions 128 may be aligned with streamlinedirection 46 (e.g., the direction of airflow). For example, a lengthdimension (e.g., length l, illustrated in FIG. 16) may be parallel withthe streamline direction 46.

Referring to FIG. 15, each protrusion 128 may include a curvedcross-sectional profile (e.g., convex-shaped) having a radius R. Aninter-region 130 of the aerodynamic surface 40 (e.g., an exteriorsurface of the sidewall 122) between adjacent (e.g., side-by-side)protrusions 128 may include a curved cross-sectional profile (e.g.,concave-shaped) opposite to the curved cross-sectional profile of theprotrusions 128. Thus, the plurality of protrusions 128 may form a wavypattern (e.g., having a waveform) on the aerodynamic surface 40.

The radius R of each protrusion 128 may be between approximately 0.12inch and 0.50, and more particularly, between approximately 0.20 inchand 0.24 inch. In an example construction, the radius R of eachprotrusion 128 may be the same. In another example construction, theradius R of one or more protrusions 128 may be different than at leastone other protrusion 128. For example, an uppermost protrusion 128 mayinclude the largest radius R and each successive protrusion 128 mayinclude a radius R equal to or smaller than the radius R of theprotrusion 128 directly above. As another example, a lowermostprotrusion 128 may include the largest radius R and each successiveprotrusion 128 may include a radius R equal to or smaller than theradius R of the protrusion 128 directly below. As another example, theradius R each protrusion 128 may be different. As yet another example,the radius R of each protrusion 128 may be randomized.

Referring to FIG. 16, each protrusion 128 may gradually increase inheight h as the protrusion approaches the aperture 76. The height h maybe between approximately 0.08 inch and 0.22 inch. In an exampleconstruction, the height h of each protrusion 128 may be the same. Inanother example construction, the height h of one or more protrusions128 may be different than at least one other protrusion 128. In yetanother example construction, the height h of each protrusion 128 may bedifferent.

Each protrusion 128 may include a length l as the protrusion approachesthe aperture 76. The length l may be between approximately 2 inches and3 inches. In an example construction, the length l of each protrusion128 may be the same. In another example construction, the length l ofone or more protrusions 128 may be different than at least one otherprotrusion 128. In yet another example construction, the length l ofeach protraction 128 may be different.

Accordingly, the disclosed apparatus may provide a tripod with anaerodynamic surface that positions a viewing angle of a camera to anear-optimum data collection position and controls detrimental airflowon the tripod to minimize vibrations on the camera to reduce negativeimpact on image quality. A camera fairing with an aerodynamic surfacemay surround the camera to reduce vibrations, pressure variations or anyother undesirable signal to optimize image quality. In the aerospaceexample, the apparatus may be attached in a manner suitable to achievesystem safety requirements and permit removal and/or re-installation ofthe tripod and/or the camera.

Referring to FIG. 17, one embodiment of a method, generally designated200, for monitoring at least one performance characteristic of a wingassembly of an aircraft may begin with the step of connecting a tripodto an exterior surface of the aircraft, as shown at block 202. Thetripod may include a plurality of airfoils defining an aerodynamicsurface of the tripod.

As shown at block 204, the camera may be mounted within a sealedinternal volume of a camera enclosure and the camera enclosure may beconnected to the tripod.

As shown at block 206, a camera may be positioned on the tripod at apredetermined non-zero viewing angle directed toward the wing assembly.

As shown at block 208, a camera fairing may be connected to the tripodsurrounding the camera and/or the camera and camera enclosurecombination. The camera fairing may include a sidewall defining anaerodynamic surface of the camera fairing, an aperture disposed throughthe sidewall and aligned with the camera and a plurality of protrusionspositioned proximate (e.g., at or near) the aperture.

As shown at block 210, the sealed internal volume of the cameraenclosure may be purged, for example by a dry nitrogen source.

As shown at block 212, at least one performance characteristic of thewing assembly may be recorded during flight of the aircraft.

Although various embodiments of the disclosed apparatus have been shownand described, modifications may occur to those skilled in the art uponreading the specification. The present application includes suchmodifications and is limited only by the scope of the claims.

What is claimed is:
 1. An apparatus for monitoring at least oneperformance characteristic of a component of a vehicle, said apparatuscomprising: a tripod comprising an aerodynamic surface, said tripodfurther comprising: a first leg directed toward a forward end of saidvehicle; a second leg directed toward an aft end of the vehicle; and athird leg directed toward said aft end of said vehicle, wherein: each ofsaid first leg, said second leg and said third leg comprises an airfoil;said airfoil of each of said first leg, said second leg and said thirdleg defines said aerodynamic surface of said tripod; each of said firstleg, said second leg and said third leg are disposed at a non-zero sweepangle with respect to a plane normal to a streamline direction; saidthird leg is offset with respect to said second leg; and said second legand said third leg are disposed at a non-zero splay angle with respectto one another.
 2. The apparatus of claim 1 further comprising a camerapositioned on an upper end of said first leg at a viewing angle.
 3. Theapparatus of claim 2 further comprising a camera fairing connected tosaid first leg and surrounding said camera.
 4. The apparatus of claim 3wherein said camera fairing comprises: a sidewall comprising anaerodynamic surface; and an aperture disposed through said sidewall,wherein said aperture is aligned with said camera.
 5. The apparatus ofclaim 4 wherein said aerodynamic surface of said camera fairingcomprises a plurality of protrusions positioned proximate said aperture.6. The apparatus of claim 5 wherein each protrusion of said plurality ofprotrusions adjoins an adjacent one of said plurality of protrusions. 7.The apparatus of claim 1 wherein said airfoil comprises a leading edgeand a trailing edge, and wherein said leading edge of said airfoil ofeach of said first leg, said second leg and said third leg is orientedin said streamline direction.
 8. The apparatus of claim 1 furthercomprising a camera enclosure connected to said first leg, said cameraenclosure comprising a plurality of sidewalls defining a sealed internalvolume, wherein said camera is mounted within said sealed internalvolume of said camera enclosure, and wherein said camera fairing isconnected to said first leg surrounding said camera enclosure.
 9. Theapparatus of claim 8 further comprising a dry nitrogen source fluidlyconnected to said internal volume of said camera enclosure.
 10. Theapparatus of claim 8 wherein: each of said first leg, said second legand said third leg further comprises a support strut mounted within saidairfoil; said camera enclosure is connected to an upper end of saidstrut of said first leg; and said camera fairing is connected to anupper end of said airfoil of said first leg surrounding said cameraenclosure.
 11. The apparatus of claim 1 wherein: said vehicle comprisesan aircraft and said component comprises a wing assembly of saidaircraft; each of said first leg, said second leg, and said third leg isnon-rigidly connected to an exterior surface of said aircraft; and saidcamera is positioned at a predetermined viewing angle directed towardsaid wing assembly.
 12. The apparatus of claim 1, wherein said airfoilof each of said first leg, said second leg and said third leg has asymmetric cross-sectional shape.
 13. A method for monitoring at leastone performance characteristic of a wing assembly of an aircraft, saidmethod comprising: connecting a tripod to an exterior surface of saidaircraft, said tripod comprising a plurality of airfoils defining anaerodynamic surface of said tripod; positioning a camera on said tripodat a predetermined viewing angle directed toward said wing assembly;connecting a camera fairing to said tripod surrounding said camera, saidcamera fairing comprising a sidewall defining an aerodynamic surface ofsaid camera fairing, an aperture disposed through said sidewall andaligned with said camera and a plurality of protrusions positionedproximate said aperture; and recording said at least one performancecharacteristic of said wing assembly during flight.
 14. The method ofclaim 13 wherein said tripod further comprises: a first leg directedtoward a forward end of said aircraft; a second leg directed toward anaft end of said aircraft; and a third leg directed toward said aft endof said aircraft.
 15. The method of claim 14 wherein each of said firstleg, said second leg and said third leg are disposed at a non-zero sweepangle with respect to a plane normal to a streamline direction.
 16. Themethod of claim 15 wherein said third leg is offset with respect to saidsecond leg.
 17. The method of claim 16 wherein said second leg and saidthird leg are disposed at a non-zero splay angle with respect to oneanother.
 18. The method of claim 13 wherein each protrusion of saidplurality of protrusions adjoins an adjacent one of said plurality ofprotrusions.
 19. The method of claim 13 further comprising: mountingsaid camera within a sealed internal volume of a camera enclosure;connecting said camera enclosure to said tripod; and purging said sealedinternal volume of said camera enclosure.
 20. The method of claim 19wherein said purging comprises supplying dry nitrogen to said sealedinternal volume.